Device for locking an engine on an aircraft pylon

Abstract

A device for locking an engine on a pylon includes two systems attaching the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine. A second region is adjacent to a center of gravity plane of the engine and closer to a fan than a first region. A first system attaching to the first region is rigid towards torsional, transverse and vertical engine forces. The first region is located at a separation between two compressors of the engine or two turbines, whether the fan is at a rear or front of the engine respectively, the separation being adjacent to a node of a first engine flexural mode. A second system attaching to the second region is rigid towards transverse and vertical forces but less rigid than the first system. The device also includes a third system withstanding thrust forces in the longitudinal direction.

The invention claimed is: 
     
       1. A device for locking an engine on an aircraft pylon, comprising:
 two systems that attach the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine and of the aircraft, the attachment regions including a first front region and a second region, the second region placed adjacent to a plane of a center of gravity of the engine and closer to a fan than the first region, wherein
 a first system of the two systems that attaches to the first region is rigid towards torsional, transverse and vertical forces exerted by the engine, the first region is located at a location of a separation between two compressors of the engine or two turbines depending on whether the fan is at a rear or at a front of the engine respectively, said separation being adjacent to a node of a first engine flexural mode, and 
 a second system of the two systems that attaches to the second region is rigid towards transverse and vertical forces but less rigid than the first system that attaches to the first region, and 
 
 the device comprises a third system that withstands thrust forces in the longitudinal direction. 
 
     
     
       2. The locking device according to  claim 1 , wherein the second region is located between the turbines or the compressors of the engine and the fan, depending on whether the fan is at the rear or at the front of the engine respectively. 
     
     
       3. The locking device according to  claim 1 , wherein the third system that withstands the thrust forces comprises a connecting rod connecting the pylon to the engine. 
     
     
       4. The locking device according to  claim 3 , wherein the connecting rod runs down from the pylon to the engine from a location adjacent to the first region to a location adjacent to the second region and is directed towards an intersection between the axis of the engine and a plane of the second region. 
     
     
       5. The locking device according to  claim 1 , wherein the second system that attaches to the second region comprises flexible connections. 
     
     
       6. The locking device according to  claim 1 , wherein the pylon comprises a portion that connects to the second system that attaches to the second region which is more flexible than a main portion of the pylon, to which the first system that attaches to the first region is joined. 
     
     
       7. The locking device according to  claim 1 , wherein the locking device is isostatic. 
     
     
       8. An aircraft, wherein the aircraft comprises a locking device according to any of the preceding claims. 
     
     
       9. A device for locking an engine on an aircraft pylon, comprising:
 two means for attaching the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine and of the aircraft, the attachment regions including a first front region and a second region, the second region placed adjacent to a plane of a center of gravity of the engine and closer to a fan than the first region, wherein
 a first means for attaching to the first region, of the two means, is rigid towards torsional, transverse and vertical forces exerted by the engine, the first region is located at a location of a separation between two compressors of the engine or two turbines depending on whether the fan is at a rear or at a front of the engine respectively, said separation being adjacent to a node of a first engine flexural mode, and 
 a second means for attaching to the second region, of the two means, is rigid towards transverse and vertical forces but less rigid than the first means for attaching to the first region, and 
 
 the device comprises a means for withstanding thrust forces in the longitudinal direction.